Research on Vibration Load Spectrum of Aero Engine Control System Based on Fatigue Damage Equivalence

As a key part of aero engine, the control system must be reliable to ensure safe flight. Based on the principle of fatigue damage equivalence, a new method for compiling vibration load spectrum was proposed by deriving life cycle measurement spectrum calculation formula. By collecting the vibration data of control system, a life cycle vibration load spectrum and standard vibration load spectrum based on fatigue damage equivalence was compiled. In order to accelerate fatigue test, also avoid over-test or under-test, the method of compiling accelerated vibration load spectrum based on fatigue damage equivalence was also researched. Compared to traditional methods based on power equivalence, method proposed in this paper pays more attention to realize the fatigue damage in the experimental environment consistent with the actual working environment. This contributes to reliability analysis, fatigue life prediction and maintenance strategy design of aero engine control system under vibration conditions.